| 摘要 |
<p>The invention relates to an impeller for a turbine engine, such as a turbojet engine or a turboprop engine of an aircraft, intended for rotating about an axis of rotation in a predetermined direction of rotation (R) and for having a flow of gas passing therethrough, comprising a series of blades (7) distributed circumferentially about the axis of rotation of the wheel, the radially external end of each blade (7) comprising a heel (11) supporting at least one radially external lip (12, 13), extending circumferentially in an oblique direction (α1, α2) relative to the radial plane (P) perpendicular to the axis of rotation, the lip (12, 13) being angled circumferentially in the downstream direction in the aforementioned direction of rotation (R) such as to enable a compression of the gases located upstream from the lip (12, 13) during the rotation of the impeller (1).</p> |
